KR20150018017A - Apparatus for combustion diagnostic of gas turbine - Google Patents

Abstract

The present invention relates to a combustion diagnosis apparatus of a gas turbine, which can accurately diagnose a combustion state of a combustor by measuring dynamic pressure, static pressure and a self-luminous signal of flame inside a combustion chamber simultaneously. The combustion diagnosis apparatus of a gas turbine according to the present invention comprises: a combustion diagnosis tube; a pressure sensor measuring the dynamic pressure and the static pressure of the combustion chamber from an acoustic wave signal; a first optical dichroic mirror; a second optical dichroic mirror; a third optical dichroic mirror; a first photomultiplier tube; a second photomultiplier tube; a third photomultiplier tube; and a control unit diagnosing a combustion state of the combustion chamber by analyzing the dynamic pressure and the static pressure measured by the pressure sensor, CH radical information measured by the first photomultiplier tube, OH radical information measured by the second photomultiplier tube, and C2 radical information measured by the third photomultiplier tube.

Description

TECHNICAL FIELD [0001] The present invention relates to a gas turbine combustion diagnosis apparatus,

The present invention relates to a gas turbine combustion diagnosis apparatus.

In a gas turbine power generation system, combustor burnout accidents are frequent due to unstable combustion. Therefore, a dynamic pressure sensor is installed to monitor and control the dynamic pressure and the dynamic pressure is analyzed to take appropriate measures when a signal exceeding a certain dynamic pressure is detected. However, it is difficult to accurately diagnose combustion instability by monitoring only the combustion dynamic pressure, because disturbance factors causing combustion instability may be various causes such as fuel quality imbalance, driver malfunction, changes in atmospheric temperature and humidity, and aging of equipment.

In recent years, the integrated gasification combined cycle (IGCC) technology has attracted a great deal of attention, and the fluctuation of the shear pressure is caused when the syngas is supplied from the gas turbine power generation system to the gas turbine, The necessity of combustion diagnosis is more emphasized. In addition, recently, various power generation fuels such as Biogas, DME (Dimethyl Ether) and SNG (Synthetic Natural Gas) and renewable energy are applied to gas turbines. Since the combustion phenomenon greatly varies according to the characteristics of each fuel, Is required.

Korean Unexamined Patent Application Publication No. 10-2013-0003658 (2013.01.09)

The present invention provides a gas turbine combustion diagnostic apparatus capable of simultaneously measuring the dynamic pressure, the static pressure, and the self-emission signal of the flame in the combustion chamber and accurately diagnosing the combustion state of the combustor.

A gas turbine combustion diagnosis apparatus according to the present invention includes: a combustion diagnosis tube for receiving an acoustic wave signal and a self-emission signal from a flame generated in a combustion chamber; A pressure sensor installed in the combustion diagnosis tube for measuring a static pressure and a dynamic pressure of the combustion chamber from the acoustic wave signal; A first dichroic mirror installed in the combustion diagnosis tube for transmitting only light having CH radical information among the self-emission signals and reflecting the other light; A second dichroic optical mirror installed in the combustion diagnosis tube for transmitting only light having OH radical information among the light reflected from the first dichroic optical mirror and reflecting the other light; A third dichroic optical mirror installed in the combustion diagnosis tube for transmitting only light having C ₂ radical information of light reflected from the _second dichroic optical mirror; A first photomultiplier for amplifying the light transmitted through the first dichroic optical mirror and measuring CH signal information of the self luminous signal; A second photomultiplier for amplifying the light transmitted through the second dichroic optical mirror and measuring OH radical information of the self luminous signal; A third photomultiplier tube for amplifying light transmitted through the third dichroic optical mirror and measuring C ₂ radical information of the self luminous signal; And a controller for controlling the pressure and the static pressure measured by the pressure sensor, the CH radical information measured by the first photomultiplier, the OH radical information measured by the second photomultiplier, and the C ₂ radical information measured by the third photomultiplier And a controller for diagnosing the combustion state of the combustion chamber.

The combustion diagnosis tube may include a main tube connected to the combustion chamber and formed in a straight line shape; A first sub-tube protruding from one side of the main tube and connected to the main tube; A second sub tube projecting from the other side of the main tube and connected to the main tube; And an endless coil tube formed between the main tube and the first sub tube.

The first dichroic optical mirror is formed on the main tube and is located at a position farther from the position where the first sub tube, the second sub tube, and the endless coil tube project from the portion where the main tube is connected to the combustion chamber .

Further, the second dichroic optical mirror may be formed at a position where it branches from the main tube to the first sub-tube.

Also, the third dichroic optical mirror may be formed at a point where it branches from the main tube to the second sub tube.

Further, the acoustic wave signal may flow through the endless coil tube.

The first photomultiplier tube is formed at an end of the main tube, the second photomultiplier tube is formed at an end of the first subtube, and the third photomultiplier tube is connected to an end of the second subtube As shown in FIG.

In addition, the first dichroic mirror can transmit light in a wavelength band of 431 +/- 2 nm.

In addition, the second dichroic optical mirror can transmit light in a wavelength band of 309 +/- 2 nm.

In addition, the third dichroic mirror can transmit light in a wavelength band of 517 ± 2 nm.

In addition, if the difference between the static pressure of the combustion chamber and the pressure of the air flowing into the combustion chamber is less than the regulation value, the control unit may determine that the combustion state is unstable and generate an alarm.

In addition, if the difference between the static pressure of the combustion chamber and the pressure of the air flowing out of the combustion chamber is less than the regulation value, it is determined that the combustion state is unstable and an alarm can be generated.

Also, the controller analyzes the RMS (Root Means Square) value and the frequency of the dynamic pressure, and if the frequency is larger than the regulation value, it determines that the combustion state is unstable and generates an alarm.

The control unit analyzes the RMS and frequency of each of the CH radical signal, the OH radical signal and the C ₂ radical signal to calculate a Rayleigh index and a flame transfer function and a gain and a phase difference of the flame transfer function, It is possible to determine whether or not the vibration is generated and its cause, determine whether the combustion is complete, identify the cause of the incomplete combustion, and determine whether the flame is backwarded, lifted or leaned and its cause.

The gas turbine combustion diagnosis apparatus according to an embodiment of the present invention includes a pressure sensor, a dichroic optical mirror, and a photomultiplier to simultaneously measure and analyze the dynamic pressure, the static pressure, and the self-emission of the flame in the combustion chamber, . Accordingly, the gas turbine combustion diagnosis apparatus can detect the abnormal combustion symptoms early, thereby preventing burnout of the combustor in advance, and it is possible to reduce the generation of harmful exhaust emissions by deriving the optimum combustion condition at the time of combustion tuning have.

1 is a cross-sectional view showing a state where a gas turbine combustion diagnosis apparatus according to an embodiment of the present invention is mounted on a combustor.
2 is a schematic cross-sectional view showing a gas turbine combustion diagnosis apparatus according to an embodiment of the present invention.
3 is a block diagram illustrating a gas turbine combustion diagnostic apparatus according to an embodiment of the present invention.

DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, so that those skilled in the art can easily carry out the present invention.

1 is a cross-sectional view showing a state where a gas turbine combustion diagnosis apparatus according to an embodiment of the present invention is mounted on a combustor. 2 is a schematic cross-sectional view showing a gas turbine combustion diagnosis apparatus according to an embodiment of the present invention. 3 is a block diagram illustrating a gas turbine combustion diagnostic apparatus according to an embodiment of the present invention.

1 to 3, a gas turbine combustion diagnosis apparatus 100 according to an embodiment of the present invention includes a combustion diagnosis tube 110, a pressure sensor 120, a first dichroic optical mirror 130, The second dichroic optical mirror 140, the third dichroic optical mirror 150, the first photomultiplier tube 160, the second photomultiplier 170, the third photomultiplier 180, And a control unit 190.

The combustion diagnosis tube 110 is connected to the combustor 10 to receive an acoustic wave signal W and a chemiluminescence signal L from a flame generated in the combustion chamber 20. The combustion diagnosis tube 110 includes a main tube 111, a first sub tube 112, a second sub tube 113, and an endless coil tube 114.

The main tube 111 is connected to the combustor 10 and is formed in a straight line. The main tube 111 receives the acoustic wave signal W and the self-emission signal L. And a static charge valve 111a is mounted at a portion where the main tube 111 is connected to the combustor 10. The static charge valve 110a is a valve for separating the gas turbine combustion diagnostic apparatus 100 from the combustor 10. [ That is, when maintenance of the gas turbine combustion diagnosis apparatus 100 according to an embodiment of the present invention is required, the control valve 111a may be closed and the combustion diagnosis tube 110 may be detached from the combustor 10 have.

The first sub tube 112 protrudes from one side of the main tube 111 and is connected to the main tube 111. The second sub tube 113 protrudes from the other side of the main tube 111 and is connected to the main tube 111. The first sub-tube 112 and the second sub-tube 113 are passages through which a signal of a part of the wavelength band of the self-emission signal L passes.

The endless coil tube 114 protrudes from one side of the main tube 111 and is formed between the main tube 111 and the first sub tube 113. The endless coil tube 114 is a passage through which the acoustic wave signal W entering the main tube 111 moves. The infinite coil tube 114 has a predetermined curvature at one side of the main tube 111 so as to minimize the influence of a reflected acoustic wave generated by colliding with the wall surface of the combustion diagnosis tube 110, And is twisted into a cochlea. The length of the endless coil tube 114 may be about 50 times the tube diameter. At the final stage of the endless coil tube 114, a repellent valve 114a is installed. The pressure reducing valve 114a serves to pressure release the gas turbine combustion diagnostic apparatus 100. That is, to fix the gas turbine combustion diagnosis apparatus 100, the control valve 111a is closed and the pressure reducing valve 114a is opened to reduce the internal pressure of the combustion diagnosis tube 110. [

The pressure sensor 120 is installed in the main tube 111 and measures a pressure in the combustion chamber 20 from the acoustic wave signal W. The pressure sensor 120 includes a static pressure sensor 121 and a dynamic pressure sensor 122. The static pressure sensor 121 is installed in a direction perpendicular to the main tube 111 and measures a static pressure in the combustion chamber 20 from the acoustic wave signal W. The dynamic pressure sensor 122 is installed in a direction perpendicular to the main tube 111 and measures a dynamic pressure in the combustion chamber 20 from the acoustic wave signal W. The information of the static pressure and the dynamic pressure in the combustion chamber 20 measured by the static pressure sensor 121 and the dynamic pressure sensor 122 is transmitted to the controller 190.

The first dichroic mirror 130 is positioned within the combustion diagnosis tube 110 and is formed to be inclined at a predetermined angle. Specifically, the first dichroic mirror 130 is positioned within the main tube 111, and the first sub-tube 112, the second sub-tube 112, and the third sub- (113) and the endless coil tube (114). The first dichroic mirror 130 is a mirror in which the first light emission signal L entering the main tube 111 is incident. The first dichroic optical mirror 130 transmits only the light L _{T1 in} the wavelength band of 431 ± 2 nm having the CH radical information from the self light emission signal L and the light L _R1 ). The light LT1 transmitted through the first dichroic optical mirror 130 is incident on the first photomultiplier 130. The light L _R1 reflected from the first dichroic mirror 130 is incident on the first dichroic mirror 130, 2 dichroic mirror 140 as shown in FIG.

The second dichroic optical mirror 140 is formed on one side of the combustion diagnosis tube 110. Specifically, the second dichroic mirror 140 is formed at a position where it branches from the main tube 111 to the first sub tube 112. The light L _R1 reflected from the first dichroic optical mirror 130 is incident on the second dichroic optical mirror 140. The second dichroic mirror 140 transmits only the light L _T2 having a wavelength band of 309 ± 2 nm having OH radical information among the lights L _R1 reflected from the first dichroic optical mirror 130 , And light (L _R2 ) in the other wavelength band is reflected. The light L _T2 transmitted through the second dichroic optical mirror 140 is incident on the second photomultiplier 140 and the light L _R2 reflected from the second dichroic optical mirror 140 is incident on the second dichroic optical mirror 140, Is incident on the third dichroic mirror (150).

The third dichroic mirror 150 is formed on the other side of the combustion diagnosis tube 110. Specifically, the third dichroic mirror 150 is formed at a position where it branches from the main tube 111 to the second sub tube 113. And the light L _R2 reflected from the second dichroic optical mirror 140 is incident on the third dichroic optical mirror 150. The third dichroic mirror 150 transmits only the light L _{T3 in} the wavelength band of 517 ± 2 nm having the C ₂ radical information in the light L _R2 reflected from the second dichroic optical mirror 140 .

The first photomultiplier tube 160 is formed at an end of the main tube 111. Light L _T1 transmitted through the first dichroic optical mirror 130 is incident on the first photomultiplier 160. That is, light (L _T1 ) having CH radical information is incident on the first photomultiplier tube (160). At this time, an optical filter 161 is formed at the front end of the first photomultiplier tube 160 to filter the light L _T1 transmitted through the first dichroic optical mirror 130 with a clearer light. The first photomultiplier 160 amplifies the light (L _T1 ) having the CH radical information, and measures the light amount of the CH light. The information of the CH radicals measured by the first photomultiplier 160 is transmitted to the controller 190.

The second photomultiplier tube 170 is formed at an end of the first sub tube 112. Light L _T2 transmitted from the second dichroic optical mirror 140 is incident on the second photo-multiplier 170. That is, light (L _T2 ) having OH radical information is incident on the second photomultiplier tube (170). At this time, an optical filter 171 is formed at the front end of the second photomultiplier tube 170 to filter the light L _T2 transmitted from the second dichroic optical mirror 140 more clearly. The second photomultiplier 170 amplifies the light (L _T2 ) having the OH radical information, and measures the amount of light of the OH radiation. The information of the OH radical measured by the second photomultiplier 170 is transmitted to the controller 190.

The third photomultiplier tube 180 is formed at an end of the second sub tube 113. Light (L _T3 ) transmitted from the third dichroic mirror (150) is incident on the third photoelectric multiplier (180). That is, light (L _T3 ) having C ₂ radical information is incident on the third photomultiplier tube (180). At this time, an optical filter 181 is formed at the front end of the third photoelectric tube 180 so as to more clearly filter the light L _T3 transmitted through the third dichroic mirror 150. The third photomultiplier 180 amplifies the light (L _T3 ) having the C ₂ radical information and measures the amount of C ₂ -mode emission. The information of the C ₂ radical measured by the third photomultiplier 180 is transmitted to the controller 190.

The controller 190 controls the pressure sensor 120 to measure the pressure and pressure information measured by the pressure sensor 120 and the information on the CH radical measured by the first photomultiplier 160, The information of the OH radical and the information of the C ₂ radical measured by the third photomultiplier 180 are converted into digital signals and analyzed to diagnose the combustion state of the combustor 10. That is, the control unit 190 analyzes the self-emission signal L of the dynamic pressure, the static pressure, and the flame in the combustion chamber 20 to diagnose the combustion state of the combustor 10. The control unit 190 may include a signal processor 191 for converting the information of the dynamic pressure, the positive pressure and the self-emission signal L into a digital signal, and a computer 192 for analyzing the digital signal.

The control unit 190 may analyze the dynamic pressure signal to diagnose the combustion state. Specifically, the controller 190 analyzes the Root Means Square (RMS) value and the frequency of the dynamic pressure signal. If the frequency is greater than the regulation value, the controller 190 determines that the combustion state is unstable and generates an alarm.

In addition, the controller 190 may analyze the positive pressure signal to diagnose the combustion state. Specifically, when the difference between the static pressure in the combustion chamber 20 and the pressure of the air flowing into the combustion chamber 20 is smaller than the regulated value, the controller 190 determines that the combustion state is unstable and generates an alarm. In addition, if the difference between the static pressure in the combustion chamber 20 and the pressure of the air flowing out of the combustion chamber 20 is smaller than the regulation value, the controller 190 determines that the combustion state is unstable and generates an alarm.

Also, the controller 190 may analyze the self-emission signal L of the flame to diagnose the combustion state. Specifically, the controller 190 may calculate the Rayleigh Index by analyzing the RMS and frequency of the CH radical signal, the OH radical signal, and the C ₂ radical signal, respectively, and may calculate the phase difference and the gain from the flame transfer function Can be calculated. Accordingly, the control unit 190 can determine whether or not the combustion vibration is generated and the cause of the combustion, and can determine whether the combustion is complete or incomplete. In addition, the control unit 190 can determine whether flame backlash, lifting, or flame occurs and causes of occurrence. In addition, the control unit 190 can determine whether or not harmful exhaust emissions such as nitrogen oxides (NOx), carbon monoxide (CO), and the like are generated. In addition, the control unit recognizes such a cause, and generates an alarm, issues a control command, and informs whether maintenance is required. Also, the control unit provides feedback such as an alarm, a load detection, and a trip according to a combustion state.

As described above, the gas turbine combustion diagnosis apparatus 100 according to an embodiment of the present invention simultaneously measures and analyzes the self-emission of the dynamic pressure, the static pressure, and the flame in the combustion chamber 20 to clearly identify the state of the flame, It is possible to prevent the burnout of the combustor 10 beforehand and to detect the optimum combustion condition at the time of the combustion tuning to reduce the generation of harmful exhaust emissions.

It is to be understood that the present invention is not limited to the above-described embodiment, and that various modifications and variations of the present invention are possible in light of the above teachings, It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.

100: Gas turbine combustion diagnostic device 110: Combustion diagnostic tube
120: pressure sensor 130: first dichroic optical filter
140: second dichroic optical filter 150: third dichroic optical filter
160: first photomultiplier 170: second photomultiplier
180: Third photoelectricity pipe 190:

Claims (16)

A combustion diagnosis tube for receiving an acoustic wave signal and a self-emission signal from a flame generated inside the combustion chamber;
A pressure sensor installed in the combustion diagnosis tube for measuring a static pressure and a dynamic pressure of the combustion chamber from the acoustic wave signal;
A first dichroic mirror installed in the combustion diagnosis tube for transmitting only light having CH radical information among the self-emission signals and reflecting the other light;
A second dichroic optical mirror installed in the combustion diagnosis tube for transmitting only light having OH radical information among the light reflected from the first dichroic optical mirror and reflecting the other light;
A third dichroic optical mirror installed in the combustion diagnosis tube for transmitting only light having C ₂ radical information of light reflected from the _second dichroic optical mirror;
A first photomultiplier for amplifying the light transmitted through the first dichroic optical mirror and measuring CH signal information of the self luminous signal;
A second photomultiplier for amplifying the light transmitted through the second dichroic optical mirror and measuring OH radical information of the self luminous signal;
A third photomultiplier tube for amplifying light transmitted through the third dichroic optical mirror and measuring C ₂ radical information of the self luminous signal; And
Wherein the first and second photomultiplier tubes measure the dynamic pressure and the static pressure measured by the pressure sensor, the CH radical information measured at the first photomultiplier, the OH radical information measured at the second photomultiplier, and the C ₂ radical information measured at the third photomultiplier tube And a controller for analyzing the combustion state of the combustion chamber to diagnose the combustion state of the combustion chamber. The method according to claim 1,
The combustion diagnostic tube
A main tube connected to the combustion chamber and formed in a straight line shape;
A first sub-tube protruding from one side of the main tube and connected to the main tube;
A second sub tube projecting from the other side of the main tube and connected to the main tube; And
And an infinite coil tube formed between the main tube and the first sub-tube. 3. The method of claim 2,
The first dichroic mirror is formed on the main tube and is formed at a position farther from the position where the first sub tube, the second sub tube, and the endless coil tube project from the portion where the main tube is connected to the combustion chamber Characterized in that the gas turbine combustion diagnostic apparatus comprises: 3. The method of claim 2,
And the second dichroic optical mirror is formed at a point where it branches from the main tube to the first sub-tube. 3. The method of claim 2,
And the third dichroic optical mirror is formed at a point where it branches from the main tube to the second sub-tube. 3. The method of claim 2,
And the acoustic wave signal flows through the endless coil tube. 3. The method of claim 2,
Wherein the first photomultiplier tube is formed at an end of the main tube. 3. The method of claim 2,
And the second photomultiplier tube is formed at an end of the first sub-tube. 3. The method of claim 2,
And the third photomultiplier tube is formed at an end of the second sub tube. The method according to claim 1,
Wherein the first dichroic optical mirror transmits light in a 431 +/- 2 nm wavelength band. The method according to claim 1,
And said second dichroic optical mirror transmits light in a wavelength band of 309 +/- 2 nm. The method according to claim 1,
And said third dichroic optical mirror transmits light in a wavelength band of 517 ± 2 nm. The method according to claim 1,
Wherein the control unit determines that the combustion state is unstable and generates an alarm when the difference between the static pressure of the combustion chamber and the pressure of the air flowing into the combustion chamber is less than the regulation value. The method according to claim 1,
Wherein the control unit determines that the combustion state is unstable and generates an alarm if the difference between the static pressure of the combustion chamber and the pressure of the air flowing out of the combustion chamber is less than the regulation value. The method according to claim 1,
Wherein the control unit analyzes an RMS (Root Means Square) value and a frequency of the dynamic pressure, and if the frequency is greater than the regulation value, the control unit determines that the combustion state is unstable and generates an alarm. The method according to claim 1,
The control unit analyzes the RMS and frequency of each of the CH radical signal, the OH radical signal and the C ₂ radical signal to calculate the Rayleigh index, the flame transfer function, and the gain and phase difference of the flame transfer function, And determining the cause of the incomplete combustion, and determining whether the flame is backwarded, lifted or lean, and causes thereof.

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